Fast starting turbine for a projectile fuse



p 1968 J. RABINOW 3,401,635

FAST STARTING TURBINE FOR A PROJECTILE FUSE Filed June 22, 1951 ""Fic'. a-

Fig.1- 9

INVENTOR. k I g g WW??? 1 Jacob Hub-1n uw ATTORALEYS 3,401,635 FAST STARTING TURBINE FOR A PROJECTILE FUSE Jacob Rabinow, Takoma Park, Md., assignor to the United States of America as represented by the Secretary of the Army Filed June 22, 1951, Ser. No. 233,095 2 Claims. (Cl. 10270.2)

The invention described in the specification and claims may be manufactured and used by or for the Government for governmental purposes without the payment to me of any royalty thereon.

This invention relates to fuses for explosive missiles and more particularly to fuses of the class which incorporate turbine means fordriving an electrical generator.

In fuses of the class referred to above a longitudinal duct is formed in the nose of the fuse through which air passes while the missile is in flight to drive a turbine coupled to an electrical generator. It is essential that the generator be brought up to operating speed as quickly as possible. In view thereof, the prime object of the invention is a new and novel means for instantly bringing the generator speed up to operating condition upon firing or launching of the missile.

Another object of the invention is a turbine driven generator in which the operation of the turbine is independent of the missiles air travel.

A further object of the invention is means, which are automatically removed at the instant of firing, for sealing and moisture proofing the air ducts.

The specific nature of the invention as well as other objects and advantages thereof will clearly appear from the following description and accompanying drawings in which:

FIG. 1 is a longitudinal sectional view of the fuse embodying the invention.

FIG. 2 is a fragmentary sectional view showing a rocket launcher tube and a rocket therein incorporating the device of the invention, but provided with a modified striker means.

FIG. 3 is an enlarged fragmentary sectional view showing the details of the modified striker means of FIG. 2.

FIG. 4 is a view similar to that of FIG. 2, but illustrating the use of electrical means for igniting the primer.

FIG. 5 is an enlarged fragmentary sectional view of the means of FIG. 4.

FIG. 6 is an enlarged fragmentary sectional view of the device of the invention showing means whereby the operation of the turbine is entirely independent of the missiles air travel.

Referring now to the drawings and first to FIG. 1 wherein 1 generally indicates an electronic type of fuse affixed to the body of an explosive projectile 2. A longitudinal bore 3, formed in the cap member 4 of the fuse, has fixed in one end thereof a releasable primer striker means 5. Positioned in the bore 3 are a primer 6 and a high pressure gas producing charge 7 having a longitudinal gas passage 8.

The striker means is conventionally maintained in safe position by means of a safety pin 9 and is provided with a shear pin 10. The opposite end of bore 3 communicates with a multiplicity of ducts 11 disposed about the periphery of a turbine 12 and having exhaust parts 13 in the peripheral surface of the cap member 4. Each of the ports 13 is provided with a plug 14 releasably held therein by means of a cement 15 to prevent foreign matter from entering the ports. The turbine 12 is mounted in the cap member 4 and coupled, by means of a coupling member 16, to an electric generator 31 mounted in the base member 17 of the fuse. The generator 31 supplies power, by means of lead 18 and 19, to an electronically controlled nited States Patent detonator contained in a housing 20 which is fixed in a threaded, hollow extension 21 of the base member 17 which is in threaded engagement with the body of the explosive projectile 2 having an explosive charge 22 therein.

When the projectile is fired from a gun the forces of setback causes the striker means to shear the shear pin and strike the primer which in turn ignites the high pressure gas producing means. The expanding gases produced by the gas producing means travel in both directions in the bore 3 and ejects the striker means and sealing plugs from the cap member. In passing rearwardly through the bore and ducts, the gases impinge upon the turbine causing it to come up to speed in a fraction of a second. When the gas pressure has been expended, the passage of air rearwardly through the bore and ducts causes the turbine to maintain its rotational speed due to the passage of the projectile relative to the medium in which it travels.

When a fuse employing the present invention is incorporated in a rocket type of missile, a modification of the striker means is required, one form of which is illustrated in FIGS. 2 and 3 wherein the tube 23 of a rocket launcher is provided with a spring biased contact arm 24 extending interiorly of the tube in alignment with the striker means of the fuse. The modified striker means of the invention comprises a plug 25 releasably fixed in the bore 3 of the cap member 4 and a spring biased striker 26 which is slidable in a bore 27 formed in the plug 25. One end 28 of the striker 26 extends exteriorly of the plug and forwardly of the cap member for contact with the arm 24. When the rocket is launched, the striker contacts the arm and is driven inwardly of the cap member to strike the primer which in turn ignites the gas producing charge 7. The striker means is subsequently ejected from the cap member as described in connection with FIG. 1.

FIGS. 4 and 5 show another modification of the invention wherein an electrical squib 29 is employed to ignite the gas producing charge 7. In this modification the plug 25 with its spring biased striker 26 is positioned in an electrical insulating sleeve 30 which is releasably fixed in the bore 3. When the rocket is launched, the striker member engages the arm 24 of the launcher and is driven inwardly of the fuse by the arm to make contact with the electrical primer 29, completing the electrical circuit and thereby functioning the primer. The circuit is formed by the rocket in contact with the launcher which is in turn connected to a battery 31 having contact with the arm 24 which completes the circuit upon engagement with the striker.

Under certain conditions it has been found desirable that the operation of the turbine be made entirely independent of the medium through which the missile passes. To accomplish this the striker means is affixed in the cap member 4, as for example by threaded engagement of the means and bore as shown in FIG. 6, so that the entire force produced by the gas producing means is applied to the turbine.

While specific embodiments have been shown and described, it will, of course, be understood that various other modifications may be made without departing from the invention. The appended claims are therefore intended to cover any such modifications within the true spirit and scope of the invention.

I claim:

1. An electrically actuated fuse for explosive missiles, comprising in combination a housing having a cap member aflixed to a base member, a turbine in the cap member coupled to an electric generator in the base member, a longitudinal bore in the cap member, striker means releasably fixed in one end of said bore, air ducts formed in the cap member in communication with the opposite end of the bore, a primer and high pressure gas producing cation with the ducts, sealing means in said ports, said 5 striker in response to forces of setback functioning the primer and causing the gas producing means to eject said striker and sealing means whereupon said turbine 0b tains operating speed due to passage of the high pressure gases through said ducts.

2. The invention in accordance with claim 1 wherein the striker means is non-releasably fixed in said bore, said striker means comprising a plug member in threaded engagernent with said bore and a spring bias striker slidably supported by said plug in alignment with said primer.

References Cited UNITED STATES PATENTS 1,310,892 7/1919 Schneider 102-852 2,457,833 1/1949 Redding 6039.47 2,468,120 4/ 1949 Senn 102-70.2 10 2,511,872 6/1950 Parker 10270.2 2,559,006 7/1951 Clapham 60-39.47

BENJAMIN A. BORCHELT, Primary Examiner. D. D. DOTY, Assistant Examiner. 

1. AN ELECTRICALLY ACTUATED FUSE FOR EXPLOSIVE MISSILES, COMPRISING IN COMBINATION A HOUSING HAVING A CAP MEMBER AFFIXED TO A BASE MEMBER, A TURBINE IN THE CAP MEMBER COUPLED TO AN ELECTRIC GENERATOR IN THE BASE MEMBER, A LONGITUDINAL BORE IN THE CAP MEMBER, STRIKER MEANS RELEASABLY FIXED IN ONE END OF SAID BORE, AIR DUCTS FORMED IN THE CAP MEMBER IN COMMUNICATION WITH THE OPPOSITE END OF THE BORE, A PRIMER AND HIGH PRESSURE GAS PRODUCING MEANS POSITIONED IN THE BORE IN COOPERATIVE RELATIONSHIP TO THE STRIKER AND THE TURBINE, THE AIR DUCTS BEING SPACED 